CN108190044B - Method for assembling all-axial thermal protection component for aircraft assembly - Google Patents
Method for assembling all-axial thermal protection component for aircraft assembly Download PDFInfo
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- CN108190044B CN108190044B CN201711269425.2A CN201711269425A CN108190044B CN 108190044 B CN108190044 B CN 108190044B CN 201711269425 A CN201711269425 A CN 201711269425A CN 108190044 B CN108190044 B CN 108190044B
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- thermal protection
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- protection component
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- 238000009434 installation Methods 0.000 claims description 15
- 230000037250 Clearance Effects 0.000 claims description 3
- 210000001503 Joints Anatomy 0.000 claims description 3
- 230000035512 clearance Effects 0.000 claims description 3
- 230000001276 controlling effect Effects 0.000 claims description 2
- 238000003032 molecular docking Methods 0.000 claims 2
- 239000000463 material Substances 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 2
- 238000005259 measurement Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 229910000838 Al alloy Inorganic materials 0.000 description 1
- 229910000831 Steel Inorganic materials 0.000 description 1
- 229910045601 alloy Inorganic materials 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- REDXJYDRNCIFBQ-UHFFFAOYSA-N aluminium(3+) Chemical class [Al+3] REDXJYDRNCIFBQ-UHFFFAOYSA-N 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 230000000875 corresponding Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 230000001681 protective Effects 0.000 description 1
- 238000004513 sizing Methods 0.000 description 1
- 239000010959 steel Substances 0.000 description 1
Images
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/10—Manufacturing or assembling aircraft, e.g. jigs therefor
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
Abstract
The invention discloses an assembling method of an all-axial thermal protection component for aircraft assembly, which comprises the following steps: scanning the molded surface of the cabin before installing the thermal protection members, determining the assembly sequence and relationship of the thermal protection members, assembling the aircraft to a turnover tool, designing a limiting block according to a theoretical gap between two adjacent thermal protection members, and sequentially installing the thermal protection members according to the assembly sequence; the invention realizes the accurate positioning and bonding links of the thermal protection component, ensures the realization of the accurate assembly method of the thermal protection structure, realizes the accuracy of the protection position, and has strong operability through the verification of the flow scheme.
Description
Technical Field
The invention belongs to the field of assembly of thermal protection systems, and particularly relates to an assembly method of an all-axial thermal protection component for aircraft assembly.
Background
In recent years, with the increasing improvement of flying parameters such as the flying height, the range, the mach number and the like of the missile, the flying load such as the bearing force, the heat, the noise, the vibration and the like is severer, the external shape of the missile body is complicated, the volume is large, the weight is light, and the problem is that a high-temperature resistant heat protection material (called a heat protection member for short) is used in a large area, and the heat protection member has the problems of low density, poor impact resistance, no pressure resistance and the like, so that the real-time protection is required in the processes of bonding, reloading and the like, and the assembly parameters (gaps, step differences and the like) are required to be strictly controlled in the design state.
Some aircraft need be through the hot test trial before flight test, relates to aircraft Y to two orientation states, and its test equipment is located the height aloft, and operation and inconvenient, the precision of assembly is difficult to guarantee, and simultaneously, the whole hot protective member that bonds in aircraft surface is difficult to directly hang on the aircraft surface.
When the aircraft operates on the ground, the aircraft has complex profile and large volume, simultaneously has the requirement of sizing and curing, is similar to the structure of a high-temperature alloy cover plate, is arranged on the lower surface of the aircraft cabin body, cannot ensure the accurate assembly of the aircraft cabin body in the X, Y and Z directions, and cannot meet the requirement of reserved gaps caused by thermal expansion.
Disclosure of Invention
The invention aims to provide an assembling method for an all-axial thermal protection component assembled on an aircraft, and the method is used for solving the problem that the thermal protection component of the aircraft cannot be accurately assembled.
The technical scheme of the invention is as follows: an assembling method for assembling a full axial thermal protection component for an aircraft is characterized by comprising the following steps:
s1, scanning the cabin profile before installing the thermal protection component to ensure that the cabin does not exceed the tolerance and meet the profile requirement;
s2, determining the assembly sequence and relationship of the thermal protection components according to the installation requirements, and firstly installing the thermal protection components with positioning holes or the thermal protection components positioned on the front and rear end surfaces;
s3, assembling the aircraft 5 to the overturning tool 6, and controlling the aircraft to overturn to the working surface: the front end face and the rear end face of the turnover tool are of circular cross-section structures and are connected with the front end face and the rear end face of the turnover tool through a butt joint 7 on an aircraft, when the thermal protection component interferes with the turnover tool, the turnover tool is subjected to local grooving, and the installation path and the operation space of the thermal protection component are guaranteed to be met;
s4, designing limit blocks according to theoretical gaps between two adjacent thermal protection members, wherein during installation, a plurality of limit blocks are arranged between the two thermal protection members to ensure uniform installation gaps; then sequentially installing thermal protection components according to the assembly sequence;
s5, when the heat protection members in the lap joint mode are installed, firstly, overlapping but not fixing the two installed heat protection members, then installing a limiting block to ensure a gap between the heat protection members, and finally, fixing the two installed heat protection members on an aircraft; when the thermal protection member in the splicing mode is installed, the limiting block is installed in place firstly by taking the installed thermal protection member as a reference, and then the thermal protection member is installed.
Has the advantages that: the invention is based on the application of the turning tool design method and the laser scanning technology, manufactures the tool, realizes the links of accurate positioning, bonding, pressurization and the like of the thermal protection component, ensures the realization of the accurate assembly method of the thermal protection structure, the precision of the protection position, and has strong operability after the verification of the flow scheme.
Drawings
FIG. 1 is a sequence of installation of a thermal protection member;
FIG. 2 is a flow chart of an embodiment of the present invention;
fig. 3 is a schematic view of the turnover tool.
Detailed Description
The present invention will be described in further detail with reference to specific embodiments thereof for the purpose of making apparent the objects, contents and advantages thereof.
The invention provides an assembling method of an aircraft assembling all-axial thermal protection member, which takes a three-axis accurate assembling method of a thermal protection structure of an aircraft as a background, and specifically comprises the following steps:
s1, according to the installation requirement proposed by the design, the heat protection component is installed on the lower surface of the No. 2 cabin, the assembly sequence of the heat protection component is confirmed, the installation sequence is shown as the attached figure 1, and the disassembly sequence is just opposite to the assembly sequence;
s2, determining a turning tool of the aircraft in the full axial direction, wherein the turning tool 5 can clamp the aircraft 6 and drive the aircraft to rotate;
a. determining the available interface relation on the aircraft, wherein the available interfaces are the front end surface of a No. 2 cabin and the rear end surface of a No. 3 cabin;
b. because the heat protection component protrudes out of the front end face of the No. 2 cabin, when the turnover tool is designed, the turnover tool is partially grooved, and the requirement for assembling the heat protection component is ensured;
the overturning tool needs to rotate by 360 degrees, so that the front end face and the rear end face of the overturning tool adopt a circular section design mode;
considering the production period, the stock material and the processing convenience, determining that the material of the turnover tool is No. 45 steel;
considering the convenience of manual operation, optimizing a force transmission route of the turnover tool in a topological mode, and performing weight reduction design;
a three-dimensional model of the turnover tool is established, the assembly process is simulated, and the turnover tool can be used satisfactorily;
s3, when the aircraft turns to the working face, limiting the aircraft through the supporting blocks:
the turnover tool is additionally provided with a supporting function, and is not easy to fix due to the fact that the turnover tool is designed to be of a circular section, so that supporting blocks with the length of ×, the width of × and the height of 200mm × 100mm × 200mm are adopted and are arranged on two sides of the turnover tool, which are in contact with an operation platform, so that the turnover tool is limited and fixed to prevent the turnover tool;
s4, firstly installing a front thermal protection component 1 in the attached drawing 1, wherein the front thermal protection component is a lap joint type thermal protection component, utilizing left and right thermal protection components 2 installed at the left and right sides of the front thermal protection component 1, the gap between 1 and 2 in the attached drawing 1 is required to be 2mm, designing a limiting block with the length of ×, the width of × and the height of × 2mm, the width of × 4mm, selecting aluminum alloy as a material, installing the limiting block at the front, the middle and the rear positions of a butt joint gap between 1 and 2 to ensure that the installation gap is uniform, and the limiting block is L-shaped or rectangular or T-shaped.
S5, assembling the heat protection component;
installing a turnover tool on the front end face of the No. 2 cabin and the rear end face of the No. 3 cabin;
rotating the aircraft by 90 degrees;
assembling the front thermal protection member 1 in the attached drawing 1 in a lap joint mode, placing the front thermal protection member 1 in the attached drawing 1 at a corresponding position on the lower surface of the cabin body, and then installing a supporting block and a limiting block to ensure that the installation position and a gap between the front thermal protection member and other thermal protection members meet the requirements;
removing supporting block and positioning block
Before installation, the thermal protection members 2 on the left side and the right side of the thermal protection member 1 are installed, and a limit block is used during installation, so that gaps between the thermal protection members and other thermal protection members can meet requirements;
completing the assembly of the middle heat shield member 3 and the rear heat shield member 4 in fig. 1 according to the assembly sequence of fig. 1;
when the product needs to be replaced, the assembly can be carried out according to the assembly flow.
S7, judging the in-place judgment of the thermal protection component
By means of a laser scanning technology, the molded surface of the cabin body is scanned before the thermal protection component is installed, the theoretical requirement is-1 mm to 1mm, the actual measurement result is 0.3mm to-0.7 mm, and the molded surface requirement is met;
after the thermal protection member is installed, the profile of the thermal protection member is swept, the theoretical requirement is-1 mm to 1mm, the actual measurement result is 0.1mm to-0.8 mm, and the profile of the thermal protection member meets the design requirement;
meanwhile, clearance (the clearance requirement is 0.2mm to 0.5mm) and step difference requirements (reverse step difference is not allowed, and forward step difference is not more than 0.3mm) are measured by using tools such as a feeler gauge and the like, so that the assembly requirement is met.
By the aid of the method, accurate assembly of the thermal protection structure of a certain product is finally completed, success of the power-assisted flight test is achieved, and accuracy of assembly of the thermal protection structure is achieved.
Claims (6)
1. An assembling method for assembling a full axial thermal protection component for an aircraft is characterized by comprising the following steps:
s1, scanning the cabin profile before installing the thermal protection component to ensure that the cabin does not exceed the tolerance and meet the profile requirement;
s2, determining the assembly sequence and relationship of the thermal protection components according to the installation requirements, and firstly installing the thermal protection components with positioning holes or the thermal protection components positioned on the front and rear end surfaces;
s3, assembling the aircraft to the overturning tool, and controlling the aircraft to overturn to the working face: the front end face and the rear end face of the turnover tool are of circular cross-section structures and are connected with the front end face and the rear end face of the turnover tool through butt joints on the aircraft, and when the thermal protection component interferes with the turnover tool, the turnover tool is subjected to local grooving, so that the installation path and the operation space of the thermal protection component can be met;
s4, designing limit blocks according to theoretical gaps between two adjacent thermal protection members, wherein during installation, a plurality of limit blocks are arranged between the two thermal protection members to ensure uniform installation gaps; then sequentially installing thermal protection components according to the assembly sequence;
s5, when the heat protection members in the lap joint mode are installed, firstly, overlapping but not fixing the two installed heat protection members, then installing a limiting block to ensure a gap between the heat protection members, and finally, fixing the two installed heat protection members on an aircraft; when the thermal protection member in the splicing mode is installed, the limiting block is installed in place firstly by taking the installed thermal protection member as a reference, and then the thermal protection member is installed.
2. The method of assembling an aircraft with an all-axial thermal protection component according to claim 1, wherein: in S3, the selectable range of the docking interface is an aircraft lifting hole or an aircraft front and rear cabin docking hole.
3. The method as claimed in claim 1, wherein the stop block is L-shaped, rectangular or T-shaped.
4. A method of assembling an aircraft with an all-axial thermal protection member according to claim 1, 2 or 3, characterized in that: after the thermal protection component is installed, the molded surface of the thermal protection component is swept, and compared with a theoretical model, the molded surface of the thermal protection component is judged to meet the design requirement.
5. The method of assembling an aircraft with an all-axial thermal protection component according to claim 4, wherein: after the thermal protection member is installed, the clearance and the step difference are measured by the feeler gauge, and whether the assembly requirement is met or not is judged.
6. The method of assembling an aircraft with an all-axial thermal protection component according to claim 4, wherein: when the aircraft turns to the working face, the aircraft is limited through the supporting block.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711269425.2A CN108190044B (en) | 2017-12-05 | 2017-12-05 | Method for assembling all-axial thermal protection component for aircraft assembly |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711269425.2A CN108190044B (en) | 2017-12-05 | 2017-12-05 | Method for assembling all-axial thermal protection component for aircraft assembly |
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| Publication Number | Publication Date |
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| CN108190044A CN108190044A (en) | 2018-06-22 |
| CN108190044B true CN108190044B (en) | 2020-07-28 |
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Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112483521B (en) * | 2020-11-17 | 2022-05-31 | 航天特种材料及工艺技术研究所 | Tool and method for sleeving rigid thermal protection layer on unclosed equal-diameter revolving body cabin section |
| CN113021226B (en) * | 2021-03-03 | 2022-08-05 | 航天特种材料及工艺技术研究所 | Sleeving tool and sleeving method for upper closed type outer heat-proof layer of cabin section |
| CN113391598B (en) * | 2021-06-28 | 2022-09-20 | 哈尔滨工业大学 | Virtual assembly simulation method and system |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101746510A (en) * | 2010-02-03 | 2010-06-23 | 北京航空航天大学 | Assembly method of leading edge flap based on laser measuring technique |
| CN103143972A (en) * | 2013-02-27 | 2013-06-12 | 中航飞机股份有限公司西安飞机分公司 | Large-span framework-type turnover clamp |
| EP2648016A3 (en) * | 2012-04-06 | 2014-06-11 | The Boeing Company | Circumferential laser crawler |
| CN106697326A (en) * | 2015-11-06 | 2017-05-24 | 波音公司 | Advanced automated process for the wing-to-body join of an aircraft with predictive surface scanning |
-
2017
- 2017-12-05 CN CN201711269425.2A patent/CN108190044B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101746510A (en) * | 2010-02-03 | 2010-06-23 | 北京航空航天大学 | Assembly method of leading edge flap based on laser measuring technique |
| EP2648016A3 (en) * | 2012-04-06 | 2014-06-11 | The Boeing Company | Circumferential laser crawler |
| CN103143972A (en) * | 2013-02-27 | 2013-06-12 | 中航飞机股份有限公司西安飞机分公司 | Large-span framework-type turnover clamp |
| CN106697326A (en) * | 2015-11-06 | 2017-05-24 | 波音公司 | Advanced automated process for the wing-to-body join of an aircraft with predictive surface scanning |
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| Publication number | Publication date |
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| CN108190044A (en) | 2018-06-22 |
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